CN102658767A - Universal wheel propulsion system of aero vehicle - Google Patents
Universal wheel propulsion system of aero vehicle Download PDFInfo
- Publication number
- CN102658767A CN102658767A CN2011103026160A CN201110302616A CN102658767A CN 102658767 A CN102658767 A CN 102658767A CN 2011103026160 A CN2011103026160 A CN 2011103026160A CN 201110302616 A CN201110302616 A CN 201110302616A CN 102658767 A CN102658767 A CN 102658767A
- Authority
- CN
- China
- Prior art keywords
- paddle
- wheel
- takes turns
- transmission shaft
- sliding shoes
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Abstract
The invention relates to a propulsion system of an aero vehicle, which uses a paddle wheel driven by a power set as a main source of lift force and propulsive force, and is capable of moving vertically and back and forth in a fluid. The invention is mainly applied in the fields of aviation and navigation, and resolves the problem that propellers can not freely change the lift force and propulsive force, providing not only all the envisaged advantages of flapping wings, but also a higher driving force than that of the flapping wings, especially a more powerful and flexible propulsive force. Multiple flight attitudes (such as left-right side tumbling, and back-forth rolling) can be easily extended. Vertical take-off and landing and hovering are the most basic functions, and performances in steady level flying, endurance, hovering in ground effect and hovering out of ground effect are significantly improved. Besides, the system provided by the invention is simple and compact in structure, and is stable, reliable and highly safe. Moreover, the type of aero vehicle has no analogues in the world so that seizing the commanding heights of the type of aero vehicle has immeasurable strategic significance in both military application and people benefits of changing human travel mode.
Description
Technical field
The present invention relates to a kind of paddle wheel that drives with engine installation as main lift and propulsive force source, can be in fluid (in the air or in the water) vertically and the propulsion system of the aviation ROV that moves forward and backward.The direction of universal conversion power on the cross section of main shaft.Be mainly used in aviation, the navigation field.
Background technology
In the present aircraft vertical flight performance with before fly performance and can not take into account, go straight up to the function vertical takeoff and landing (VTOL), but front and back flight thrust is not enough so that the permanent flat performance that flies is undesirable, duration performance is also poor.The permanent flat performance that flies of fixed-wing aircraft and cyclogyro is higher, but can not vertical takeoff and landing (VTOL) and flight backward.All use in the aircraft of screw propeller; Can not freely change easily between raising force that screw propeller produces and the propulsive force; Be A: when aircraft need rise, the screw propeller that is used to advance can not be used for the effect of driving engine raising force (mainly referring to screw propeller fixed-wing aircraft and cyclogyro here) fully.This aircraft when causing stall does not have reliable and secure guarantee.B: when aircraft when state of flight need be quickened in front and back, screw propeller but can not be used for the effect of driving engine propulsive force (only referring to propcopter and cyclogyro here) fully.This has just limited the permanent flat performance that flies of propcopter and cyclogyro.Though desired power is compared with conventional airplane and is wanted much little during the flapping flight low-speed operations; And has an excellent V ability; The wing that flapping-wing aircraft is fluttered not only produces lift, also produces propelling thrust forward, but owing to the problem of control technology, material and structure aspects fails to solve always; Flapping-wing aircraft still rests on modelling and imagination stage, and practical flapping-wing aircraft does not really create.Even if created, back and forth fluttering neither the most energy-conservation the most efficient mode of motion.In water except that above-mentioned similar principle, Submarine when be used for civilian and shallow water territory when diving short time also through compressed-air actuated mode cost height and complicated.Moreover do not have at present yet a kind of can be under water, aerial in the water, and land four vehicle of dwelling.
Summary of the invention
The present invention has overcome screw propeller can not free 360 degree conversion raising forces and the deficiency of front and back thrust; Provide a kind of paddle wheel that drives with engine installation as main lift and propulsive force source, in fluid (in the air or in the water) at any time easily 360 spend the conversion power direction promote the propulsion system of aviation ROV.The present invention not only has all advantages of the flapping-wing aircraft in the imagination, and has than flapping wing raising force more efficiently, especially more powerful propulsive force freely.Technical scheme of the present invention is to adopt a plurality of horizontal positioned and drive the aviation ROV perpendicular to the thrusts that the paddle wheel of body (paddle wheel spindle centerline perpendicular to body line of centers from front to back, and be parallel to the ground line) continuous rotation produce vertical or front and back.The paddle state controller is periodically controlled the angle that is installed in the paddle on the paddle wheel arm.To realize the needs of the feathering of paddle in different quadrants.No matter be that the paddle state controller is controlled the motion whole process of paddle, reaches lift or front and back thrust the most efficiently in rising or front and back advance.Effectively reduce the idle work that paddle wheel is done, improved the power utilization of driving engine.The parts of paddle state controller half wheel and sliding shoes are with the paddle wheel rotation, make things convenient for docking of control system and propulsion system, have increased the reliability of controlling.In sum, the technique effect of reaching is just obvious: at first be function admirable, function expansion convenient (as two-wheeled being installed in the fuselage both sides, can realize then that body original place 360 degree turn to and about rollover; If add at afterbody and to take turns, then can realize rolling before and after the fuselage; Increase the sealing in cabin and the direction control of oxygen supply and alighting gear, then can realize landly, waterborne in the air, four dwell under water.VTOL, hovering all have been the simplest basic functions, permanently flatly fly performance, duration performance, have hover in ground effect and hover out of ground effect all will be greatly improved.Next is simple and compact for structure, and reliable and stable, and is safe.Be that efficient is high once more, the paddle efficient of fluttering downwards is higher than screw propeller, and rotational efficiency is higher than reciprocal fluttering again, and the thrust of front and back just more is higher than the two.The more important thing is that the whole world does not have this type type,, still benefit the common people, change the human row mode that goes out no matter be applied to military affairs.The commanding elevation of seizing this type type technology all has immeasurable strategic importance.
Description of drawings
Observe for ease and explain following evenly with right formula wheel of the present invention explanation, levoform wheel principle is identical, just right-hand man's relation;
Fig. 1 is a vertical forces Changing Pattern scheme drawing of the present invention;
Fig. 2 is a certain serviceability of the present invention Changing Pattern scheme drawing of exerting oneself;
Fig. 3 is a front view of the present invention;
Fig. 4 is a birds-eye view of the present invention;
Fig. 5 is a left view of the present invention;
Fig. 6 is a paddle wheel structural representation of the present invention;
Fig. 7 is the arm configuration scheme drawing of taking turns of the present invention;
Fig. 8 is a paddle structural representation of the present invention;
Fig. 9 is a paddle state controller structural representation of the present invention;
Figure 10 is a paddle state controller transmission shaft structure scheme drawing of the present invention;
Figure 11 is that the present invention is applied to the transport plane imaginary drawing;
Figure 12 is that the present invention is applied to the fighter plane imaginary drawing;
Figure 13 is that the present invention is applied to fighter plane imagination birds-eye view;
Among the figure: main shaft 1, wheel hub 2, wheel arm 3, paddle 4, paddle axis hole 5, paddle shaft gear 6, controller transmission shaft bearing 7, controller transmission shaft 8, controller shaft pinion 9, controller transmission shaft big gear wheel 10, blade 11, blade frame 12, paddle axle 13, controller transmission shaft lock are protruding 14, controller transmission shaft lock spring 15, second takes turns 16, second takes turns sliding shoes 17, first takes turns 18, first takes turns sliding shoes 19, controller transmission shaft lock cross recessed 20.
The specific embodiment
Do bright specifically below in conjunction with accompanying drawing to structural principle of the present invention and principle of work:
Cardan wheel aviation ROV propulsion system of the present invention mainly is divided into paddle wheel and paddle state controller two parts constitute; Paddle wheel comprises: parts such as main shaft 1, wheel hub 2, wheel arm 3, paddle 4 constitute; By many to the wheel arm 3 around being fixed in wheel hub 2; Each overpays rotating paddle 4 to being equipped with on the wheel arm 3, and wherein each pair paddle 4 is made up of multi-disc blade 11 (keeping certain dislocation distance between the multi-disc blade 11) and a pair of blade frame 12, a pair of paddle axle 13 and bearing; The paddle state controller comprises: parts such as second takes turns 16, second takes turns sliding shoes 17, first takes turns 18, first takes turns sliding shoes 19, controller transmission shaft lock is protruding 14, the protruding spring of controller transmission shaft lock 15, controller transmission shaft big gear wheel 10, controller transmission shaft 8, controller shaft pinion 9, controller transmission shaft bearing 7 constitute; Wherein second takes turns 16, to take turns sliding shoes 17 be an integral body for second; First takes turns 18, to take turns sliding shoes 19 be an integral body for first; All be to be fixed on the frame; Do not rotate with paddle wheel; Only through its rotation of control system scalable (path of motion during adjusting is that the axle center with main shaft 1 is the circle in the center of circle), this just helps docking with control system easily and reliably, plays bridge and interface effect between control system and the propulsion system.Whole paddle state controller is being controlled the direction of paddle 4 in revolution, guarantees that 4 of paddles can produce actv. lift and thrust, and the intention that receives, transmits and implement control system, reaches the running state of control body and the purpose of attitude.The interlock mechanism of all parts is following: the moment of driving engine is passed to main shaft 1 through change speed gear box, revolves round the sun around main shaft 1 line of centers thereby take wheel hub 2, wheel arm 3, paddle 4 to.Periodically control the angle that is installed in the paddle 4 on the wheel arm 3 through the paddle state controller, with the power that realizes that 4 generations of paddle need.In paddle wheel clws rotation process, the Changing Pattern of power is during vertical uplift: like Fig. 1, when spending to 180 degree (i.e. a quadrant and a two quadrant) from 0, paddle is done displacement from top to bottom, produces raising force, is useful work, therefore will let its acting maximum.This moment, the course of action of each parts was following; First is taken turns sliding shoes 19 and pushes the mid point of controller transmission shaft lock protruding 14 to controller transmission shaft lock cross recessed 20 when 0 spends, because the recessed mid point of cross just in time is controller transmission shaft big gear wheel 10 bottom surface AnchorPoints, i.e. controller transmission shaft lock protruding 14 is coaxial concentric with controller transmission shaft big gear wheel 10; Controller transmission shaft big gear wheel 10 is just free to rotate; Because first takes turns 18, second takes turns 16 and do not participate in revolution, can tooth movement controller transmission shaft big gear wheel 10 with fast rotation, via controller transmission shaft 8, controller shaft pinion 9, paddle shaft gear 6 drive paddles 4 conter clockwises with fast rotation; On business commentaries on classics and rotation are with speed; Paddle 4 remains and is parallel to ground level so, so the main power upwards that produces in this process finishes until arriving 180 degree rotations.When spending to 360 degree (being third quadrant and four-quadrant) from 180, paddle is done from bottom to top displacement, is reseting movement, and can produce invalid decline power this moment, belongs to idle work, therefore will let its acting minimum, do not allow its acting in theory.When 180 spent, second was taken turns 16 work and accomplishes, and no longer tooth movement controller transmission shaft big gear wheel 10; Paddle 4 rotations finish, and second is taken turns sliding shoes 17 and also finishes the work, under the effect of controller transmission shaft lock spring 15; Controller transmission shaft lock protruding 14 resets; Be displaced to the cross end of controller transmission shaft lock cross recessed 20, controller transmission shaft lock protruding 14 is no longer coaxial concentric with controller transmission shaft big gear wheel 10, lockout controller transmission shaft big gear wheel 10.Paddle 4 rotation again, at this moment paddle 4 moves to 360 degree with minimum windward side all the time, and promptly paddle 4 is the tangent line of locus circle all the time in third quadrant and four-quadrant.So just, accomplish a repetition period.The Changing Pattern of the power on the horizontal direction also in like manner; During thrust before and after the needs, through operating system half wheel is rotated, (cw is for forward; Inhour is for backward) as required before and after the size of thrust confirm to rotate the angle of half wheel, thereby the proportional distribution of change lift and thrust.Angle high thrust more is big more, and the power that produces thrust distributes from raising force comes, and promptly front and back thrust and raising force are that this increases the relation that subtracts.Second is taken turns 16 and goes to third quadrant from second quadrant, and first is taken turns when first quartile goes to second quadrant, promptly two and half takes turns and clockwise rotates 90 degree simultaneously and be maximum forward speed; Otherwise two and half take turns and rotate counterclockwise 90 degree simultaneously for maximum astern speed.Thrust before and after the engine efficiency of this moment is used for fully has not a particle of raising force.If but the speed of this moment reaches the big of necessity, the raising force that fixing aileron and body produce also can balance the gravity of body.Also can rotate one of them half wheel separately, second half takes turns the motionless raising force that still produces.Rotate 90 when spending like Fig. 2 when second being taken turns 16 to third quadrant through operating system; Paddle 4 produces lift upwards in first quartile constant; The thrust that paddle 4 produces forward in third quadrant is constant, this moment difference be paddle 4 when second quadrant, promptly 90 the degree to 180 the degree between paddle 4 be the vertical line of locus circle all the time; Also be excessively to the maximum windward side of ahead power from the maximum windward side of raising force; The power that is produced then is that half is a raising force, and half is an ahead power, also is the power of 45 degree front upper places.Be all to do useful work the most efficiently in vertical direction or horizontal direction paddle 4, when resetting then with or more energy-conservation mode move, whole cardan wheel only can produce actv. lift and thrust basically.Paddle 4 adopts the dislocation arrangement architecture of multi-disc blades in addition, this structure decrease invalid resistance, improved efficient, the stability and traveling comfort and the safety that have also improved body simultaneously.
Claims (4)
1. the wheeled propulsion system of an aviation ROV; The paddle wheel that it is characterized in that driving with engine installation is as main lift and propulsive force source, (aerial or water in) rotation in fluid and produce horizontal or vertical thrust (can produce controlled 360 power spent in main axis cross section) and drive the aviation ROV; Change lift and the proportional distribution of thrust and the direction of power through control system, realize the running state and the attitude of body; Its structure be a plurality of paddle wheel horizontal positioned and perpendicular to body (the paddle wheel spindle centerline is perpendicular to body line of centers from front to back; And be parallel to the ground line); Parts comprise: parts such as main shaft 1, wheel hub 2, wheel arm 3, paddle 4 constitute, wherein wheel hub 2, wheel arm 3, with to being unit; The axial line of paddle 4 time rotationals is parallel all the time with the axial line of main shaft 1.
2. propulsion system according to claim 1; Its characteristic also be paddle wheel by many to the wheel arm 3 around being fixed in wheel hub 2; Each overpays rotating paddle 4 to being equipped with on the wheel arm 3, and wherein each pair paddle 4 is made up of multi-disc blade 11 (keeping certain dislocation distance between the multi-disc blade 11) and parts such as a pair of blade frame 12, a pair of paddle axle 13, paddle shaft gear 6 and bearing.
3. control the facing the wind direction of paddle 4 in revolution for one kind; Guarantee paddle 4 main actv. lift and the thrusts of producing; And the intention that receives transmission and enforcement control system; Reach running state and the device of attitude---the paddle state controller of control body, said device comprises: parts formations such as second takes turns 16, second takes turns sliding shoes 17, first takes turns 18, first takes turns sliding shoes 19, controller transmission shaft lock is protruding 14, the protruding spring of controller transmission shaft lock 15, controller transmission shaft big gear wheel 10, controller transmission shaft 8, controller shaft pinion 9, controller transmission shaft bearing 7; It is characterized in that second takes turns 16, second takes turns sliding shoes 17, first takes turns 18, to take turns sliding shoes 19 be to be fixed on the frame for first, with the paddle wheel revolution, only it rotates through the control system scalable, plays bridge and interface effect between control system and the propulsion system; When it rotated through the control system scalable, second took turns 16, second takes turns sliding shoes 17, first takes turns 18, to take turns sliding shoes 19 be that axial line around main shaft 1 rotates for first.
4. device according to claim 3, its characteristic are that also when first takes turns 18, second rotation that to take turns the moving rotating speed that is delivered to paddle 4 of 16 teeth be revolution and paddle 4 is with speed and reverse, promptly main shaft 1 is identical and in the opposite direction with paddle 4 rotating speeds.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011103026160A CN102658767A (en) | 2011-10-09 | 2011-10-09 | Universal wheel propulsion system of aero vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011103026160A CN102658767A (en) | 2011-10-09 | 2011-10-09 | Universal wheel propulsion system of aero vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102658767A true CN102658767A (en) | 2012-09-12 |
Family
ID=46768412
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011103026160A Pending CN102658767A (en) | 2011-10-09 | 2011-10-09 | Universal wheel propulsion system of aero vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102658767A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112298507A (en) * | 2020-10-16 | 2021-02-02 | 哈尔滨工业大学（威海） | Robot in liquid environment lower pipe based on duck foot web imitating type active steering |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB599990A (en) * | 1945-09-27 | 1948-03-25 | Cierva Autogiro Co Ltd | Improvements in helicopters |
| DE10212737A1 (en) * | 2001-11-12 | 2003-05-28 | Dieter Grimmig | Paddle-wheel drive for freighters is associated with rear of ship and adjustable in height, with paddle wheel(s) being arranged in three-dimensional frame, height adjustable with frame |
| CN1693700A (en) * | 2004-11-16 | 2005-11-09 | 俞嘉华 | Wind-mill generator combined with self rotation and revolution of wind vane for flapping-wing aircraft and its method |
| CN201390379Y (en) * | 2009-05-08 | 2010-01-27 | 山东大学 | Auto-sculling paddle wheel and associated devices for ship and motor boat |
| CN101815861A (en) * | 2007-09-06 | 2010-08-25 | 瓦特有限公司 | Energy extraction device with at least one bank of blades |
| CN101830276A (en) * | 2009-03-13 | 2010-09-15 | 蒋文禄 | Twin propellers |
-
2011
- 2011-10-09 CN CN2011103026160A patent/CN102658767A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB599990A (en) * | 1945-09-27 | 1948-03-25 | Cierva Autogiro Co Ltd | Improvements in helicopters |
| DE10212737A1 (en) * | 2001-11-12 | 2003-05-28 | Dieter Grimmig | Paddle-wheel drive for freighters is associated with rear of ship and adjustable in height, with paddle wheel(s) being arranged in three-dimensional frame, height adjustable with frame |
| CN1693700A (en) * | 2004-11-16 | 2005-11-09 | 俞嘉华 | Wind-mill generator combined with self rotation and revolution of wind vane for flapping-wing aircraft and its method |
| CN101815861A (en) * | 2007-09-06 | 2010-08-25 | 瓦特有限公司 | Energy extraction device with at least one bank of blades |
| CN101830276A (en) * | 2009-03-13 | 2010-09-15 | 蒋文禄 | Twin propellers |
| CN201390379Y (en) * | 2009-05-08 | 2010-01-27 | 山东大学 | Auto-sculling paddle wheel and associated devices for ship and motor boat |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112298507A (en) * | 2020-10-16 | 2021-02-02 | 哈尔滨工业大学（威海） | Robot in liquid environment lower pipe based on duck foot web imitating type active steering |
| CN112298507B (en) * | 2020-10-16 | 2022-06-07 | 哈尔滨工业大学（威海） | Robot in liquid environment lower pipe based on duck foot web imitating type active steering |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| AU2019203204B2 (en) | Vertical takeoff and landing (VTOL) air vehicle | |
| CN106927030B (en) | Oil-electricity hybrid power multi-rotor aircraft and flight control method thereof | |
| RU2670356C2 (en) | Aircraft capable of vertical take-off | |
| CN110077588B (en) | Sea, land and air submerged four-purpose aircraft capable of taking off and landing vertically | |
| US9616995B2 (en) | Aircraft and methods for operating an aircraft | |
| US6086016A (en) | Gyro stabilized triple mode aircraft | |
| US20200010182A1 (en) | Pivoting wing system for vtol aircraft | |
| CN106004287B (en) | Amphibious multifunctional vertical landing aircraft | |
| CN205022862U (en) | Power device and fixed wing aircraft with mechanism of verting | |
| WO2019079930A1 (en) | Sea-air-land-dive four-environment tilting three-rotor unmanned aerial vehicle capable of vertical take-off and landing | |
| CN105730692B (en) | One kind is verted the long endurance combined type aircraft of quadrotor | |
| CN201712787U (en) | Electric tilt rotor unmanned aircraft | |
| CN106864746A (en) | It is a kind of can VTOL the rotor canard configuration aircraft of tailstock formula three | |
| CN105083550A (en) | Fixed-wing aircraft realizing vertical take-off and landing | |
| CN106938701A (en) | It is a kind of can VTOL the rotor canard configuration aircraft of tailstock formula four | |
| CN101879945A (en) | Electric tilting rotor wing unmanned aerial vehicle | |
| CN205022861U (en) | VTOL fixed wing aircraft | |
| US11407506B2 (en) | Airplane with tandem roto-stabilizers | |
| US11433093B2 (en) | Compact gyroplane employing torque compensated main rotor and hybrid power train | |
| CN111498100A (en) | Thrust vector tilting three-rotor unmanned aerial vehicle and control method thereof | |
| CN106828919A (en) | It is a kind of can VTOL the coaxial Fan Jiang tailless configurations aircraft of tailstock formula | |
| CN104477373A (en) | Half-rotating-mechanism lifting-wing low-speed aircraft | |
| CN106828920A (en) | It is a kind of can VTOL tailstock formula tailless configuration aircraft | |
| CN102658767A (en) | Universal wheel propulsion system of aero vehicle | |
| CN204297057U (en) | A kind of half-rotating mechanism lift wing dopey |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20120912 |